Automatic control means for aeroplanes



March 17, 1931. 1 NORHElM 1,796,576

AUTOMATIC CONTROL MEANS FOR AEROPLANES Filed Dec. 27, 1927 2 Sheets-Sheet 1 March 17, 1931. L M, NQRHEIM 1,796,576

AUTOMATIC CONTROL MEANS FOR AEROPLANES Filed Dec. 27, 1927 2 Sheets-Sheet 2 A /\\\\IM Guam 5 Patented Mar. 17, 1931 UNITED STATES PATENT OFFICE AUTQMATIC contrac MEANS non annorranns Application filed December 27, 1927. Serial No. 242,882.

This invention relates to control means for aeroplanes and refers particularly to auto.-

matic horizontal and lateral control means therefor.

5 An object of the invention is to provide means associated with the usual manual control means whereby the aeroplane may be automatically controlled without the necessity of constantly actuating the manual con- 1G trol means.

Another object is the provision of such an automatic control means in combination with a pivotally mounted fuselage.

With these and other objects in view, the

-" invention resides in certain novel features of construction, combinations and arrangements of parts as will be more fully described and particularly pointed out in the appended claims.

In the drawings:

Figure 1 is a side elevation of an aeroplane constructed in accordance with the present invention;

Figure 2 is a transverse sectionthrough an aeroplane;

Figure 3 is a side elevation of the automatic control means;

Figure 4 is a detail view of the means for locking the automatic control means to the manual control rod;

Figure 5 is a detail view of the universal mounting for the manual and automatic control means.

In the accompanying drawings wherein like characters of reference indicate like parts, the numeral 1 designates an aeroplane comprising the transverse wings 2, the "fuselage 3 and the landi g gear The aeroplane is provided with the usual control means con- 49 sis ting of the rear elevators 5 and the ailerons '6 operable by the joy stick or control rod For connecting the controlrod to the elevators, any suitable connecting means 8 may be utilized while the usual connecting Wires or rods 8 are provided for connecting the ailerons to the control rod.

This cont-rolrod 7 is preferably suspended from auniversal mounting 9 which is supported from the longron 10. Depending 5 bearing members 10' p oject @9 1; the 1011- gron for supporting the mounting 9 which comprises an outer ring 11 provided with stub axles 12 journalled in the members 10, and an inner ring 13 provided with stub shafts 14 journalled in the outer ring at right angles to the supporting means for the outer ring.

Preferably the control rod 7 is suitably journalled in the inner ring by means of the stub axles 15 which are disposed directly in alignment with the axles 12 and therefore at right angles to the stub shafts 14. lVith this arrangement it willbe apparent that a universal movement of the control rod is permitted whereby a forward and backward movement of this rod will actuate the elevators 5 while a sidewise movement will operate the ailerons 6. A steering wheel 16 is rotatably mounted upon the control rod adjacent its free end and a pulley 17 is rigidly secured to the wheel and concentric therewith. Pullcys 18 are also mounted on the shafts 14 between the inner and outer rings and together with the pulley 17 are adapted tosuitably guide a cable 19 which extends rearwardly from the mounting 9 and 1s con nected to the rudder 20.

With the construction as thus far described, it will be apparent that a continual handling of the control rod is necessary in order to properly control the movements of the aeroplane and it will be evident that during long or continued flights that such a practice will become very fatiguing to the operator. For this reason I have provided an automatic control means for the aeroplane which may be engageable with and disengageable from the control red at will so that when desired, the operator may utilize this automatic control means and thus eliminate the necessity of constantly actuating the control rod by h and.

For accomplishing this I have provided an automatic control member 21 consisting of the side frame members 22 which are su pended from the stub shafts 14:. It will be noted that these stub shafts are extended a suitable distance outwardly from the outer ring 11 and thereby provide suitable bearing frames 22. These frames extend downwardly from the universal mounting and terminate a slight distance above the floor of the fuselage. As shown,- a seat 23 is supported between the frame members adjacent their lower ends, the arrangement being such that the control member 21 constitutes a swinging chair for the operatior of the aeroplane. Suitably mounted upon the lower end of one of the frames 22is a cam 24 to which is secured one end of a flexiblecable 25, this cable extending through a suitable opening in the frame member and being secured. at its other end to a spring pressed plunger 26 suitably mounted in theupper end of the frame. This plunger is adapted toengage a recess 27 in one of the stub shafts l l for locking the control member to the inner ring 13. The cable 25 is provided with a branch portion or extension 28 to which a second spring pressed plunger 29 is connected, this plunger being carried by the inner ring 13 and being adapted to engage a recess 39 in one of the stub axles 15 of the control rod 7. Directly below the member 21 is positioned a plate 31 supported upon the floor of the fuselage and which is adapted to be engaged by the cam 2 1 for locking the member 21 to the plate. Preferably a handle 32 is secured to the cam and is adapted to hold the same in different positions of adjustment by any suitable means 33.

lVith the construction as thus far de scribed, and assuming that the operator wishes to control'the aeroplane by means of the control rod 7, the automatic control member 22 is positioned as shown in Figure 3 with the cam member 2a engaging the plate 31 and the plunger-s 26 and 29 disengaged from their respective recesses. The control rod 7 may then be freely moved to any desirable position for controlling the elevators ailerons and rudder. However, if it is de-' sired to automatically control the aeroplane, the handle 32 is grasped by the operator moving the cam 24 upwardly out of engagement witn the plate 31, at the same time permitting the plungers 26 and 29 to engage in thelr respective recesses, thus locking the frame member to the inner ring and the in herring to the control rod ,so that the automatic control member 21 and the rod"? will move in unison." In View of the fact that the operator is seated inthe control member, it will be apparent that any movement of the aeroplane will effect a movement of the member 21, this movement being transmitted to the control rod 7 and thereby effecting a movement'of the elevators, and ailerons, to bring the aeroplane back to its normal flying position. WVhile the rudder is not automatically operated by the control member, the steering wheel 16 will always be positioned directly in front of the operator when the automatic control is in use,

so that the rudder may be operated merely by moving the steering wheel and with it the pulley 17 which will in turn effect a movement of the cable 19.

The automatic control means may be used otally mounted to the frame construction of i the wlngs so that the fuselage wlll rock relative to the wings when the automatic control member is in use. This is accomplished by suspending thefuselage fromthe front and rearmain spars 3 1 of the wing structure. Preferably the longron is provided with integral upstanding brackets 35 which are suitably journalled upon a cross shaft 36 secured between the aforesaid main spars 34. This is of course only one manner of suspending the fuselage and any other suitable means may be employed if desired.

W ith this arrangement the plate 31 is slidably mounted upon the flooring of the'fuselage, and is secured to the inner ends of a pair of cables 37. These cables pass through the sides of the fuselage over pulleys 38 and have'their end portions secured to opposite wings. Supported longitudinally of the fuselage'is a guiding rod 39 upon which the automatic control member is permitted to slide back and forth butwhich compels it to move sidewise with the fuselage when the automatic control member is in use.

lVith this arrangement it will be apparent that when'the automatic control'is not in use and is secured to the plate 31, the pressure of the cam 2 against the plate will cause the plate to be secured to the flooring of the fuselage so that the control member will in eflect, constitute 'a portion of the fuselage. Preferably the faces of the plate 31 are serrated so as to effect a firm engagement between the plate and flooring and the cam and plate.

1t will also be noted that because of the connections between the cables 37 and the plate, the fuselage will be prevented'from moving relative to the wings when the manual control means are in use. However, when ,themember21 is in use, the cam will be lifted out ofcontact with'the plate and will permit .the fuselage to swing relative to the wings with the plate 31v slidingfover the floor of the fuselage.,' The control member will be permitted to swing back and forth clear of the plate 31 and will also swing sidewise with the fuselage because of the rod 39. Thus any 'movement'of the aeroplane in any direction will function to transmit motion to the controi member which Wlll in turn operate the necessary control element for bringing the plane to an even keel.

A second cam 24 is mounted upon the opposite side of the frame from the cam 24 and is movable therewith. This provision is made so that the automatic control member will at all times be capable of attachment to the plate 31 no matter in what position the plate is upon the floor of the fuselage.

R Preferably the control means 8 has inter- 'may be easily connected to and disconnected from the usual manual control means as desired so that when the manual operation of the aeroplane becomes fatiguing the operator may merely connect the automatic means to the manual means and permit the aeroplane to be automatically controlled.

While it is believed that from the foregoing description, the nature and advantage of my inventionwill be readily apparent, I desire to have it understood that I do not limit myself to the specific construction herein shown and described and that such changes may be resorted to when desired as fall within. the scope of what is claimed.

What I claim as my invention is: i

1. In combination with an aeroplane, a manually operable control rod for said acroplane, means for movably mounting said con trol rod upon said aeroplane, automatic control means for said aeroplane supported by the aforesaid mounting means but free from engagement with said control rod, and means for detachably connecting said control means to said control rod.

2. In combination with an aeroplane, a manually operable control rod for said aeroplane, means for movably mounting said control rod upon said aeroplane, automatic control means for said aeroplane movably suspended from the aforesaid mounting means and constituting a seat for the operator of the aeroplane, and means for detachably connecting said control means to said control rod.

8. In combination with an aeroplane, a manually operable control rod for said aerO- plane, a universal mountingfrom which said control rod is suspended, and means for automatically controlling said aeroplane including a seat supporting frame suspended from said mounting.

4. In combination with an aeroplane, a manually operable control rod for said aeroplane, a universal mounting for said control rod, means for automomatically controlling said aeroplane including a frame pivotally suspended from said mounting and means for detachably connecting said frame to said control rod.

5. In combination with an aeroplane, a

manually operable control rod for said aeroplane, a universal mounting for said rod comprising an inner ring pivotally supporting said rod, an outer ring pivotally supporting said inner ring, said outer ring being pivotally supported in said aeroplane, and means for automatically controlling said aeroplane including a frame pivotally supported from said mounting and detachably connected to said control rod.

6. In combination with an aeroplane, a nanually operable control rod for said aeroplane, a universal mounting for said rod comprising an outer ring pivotally mounted in said aeroplane, an inner ring pivotally supporting said control rod and having stub shafts journalled in said outer ring, means for automatically controlling said aeroplane including a frame pivotally suspended from said stub shafts, and means carried by said fra ne for locking the same to said control rod whereby said rod and frame will move in unison.

7. In combination with an aeroplane, a

manually operable control rod for said aeroplane, a universal mounting for said rod comprising an outer ring pivotally mounted in said aeroplane, an inner ring pivotally supporting said control rod and having stub shafts journalled in said outer ring, means for automatically controlling said aeroplane including a frame pivotally suspended from said stub shafts, spring pressed plungers carried by said frame and inner ring respective ly for locking said frame to one of said stub shafts and said inner ring to said control .rod, and means carried by said frame for moving said plungers into and out oflocking position. i i

8. In combination with an aeroplane, a manually operable control rod for said aeroplane, a universal mounting for said control rod, means for automatically controlling said aeroplane including a frame pivotally suspended from said mounting, means for locking said frame to said mounting and control rod, a plate supported upon the bottom of said aeroplane below said frame and a cam member pivotally mountedupon said frame and engageable with said plate for securing the frame thereto.

9. In combination with an aeroplane, a manually operable control rod for said aeroplane, a universal mounting for said control rod, means for automatically controlling said aeroplane including a frame pivotally suspended from said mounting, means for locking said frame to said mounting and control rod, a plate supported upon the hotand fuselage.

'tom of said aeroplane, a cam carried by having transversely extending wings, a fuselage pivotally mounted centrally of said wings, a plate supported upon the floor of said fuselage, a pair ofcables attached to said plate and secured to said wings, a manually operable control rod for said aeroplane mounted centrally of said wings, means for automatically controlling said aeroplane including a frame suspended from said control rod mounting above said plate, means for locking said frame to said control rod, and means for controlling said locking means and for securing said frame to said plate 11. In combination with an aeroplane having transversely extending wings, a fuselage pivotally mounted centrally of said wings, a platesupported upon the floor of said fuselage, a pair of cables attached to said plate and secured to said wings, a man ually operable control rod for said aeroplane mounted centrally ofsaid wings, means for automatically controlling said aeroplane including a frame suspended from said control rod mounting above said plate, means for locking said frame to said control rod, and means for simultaneously securing said frame to said plate and for rendering said locking means inoperative. c

12. In combination with an aeroplane, a manually operable control rod for said aeroplane,a steering wheel movably mounted thereon, a universal mounting for said @0111 trol rod, means for automatically controlling said aeroplane including a frame pivotally suspended from said mounting, means for detachably connecting saidframe to said control rod, and a rudder controlling means for said aeroplane including a pulley carried by said steering wheel, and a cable connected to said'rudder and having portions thereof guided upon said pulley and universal mounting respectively whereby a movement of said steering wheel will actuate said rudder.

'13. In combination-with an aeroplane, a manually operable control rod for said aeroplane, a steering wheel movably mounted thereon a universal mounting for said rod comprising an inner ring pivotally supporting said rod, an outer ring pivotally supporting said inner ring, said outer ring being pivotally supported in said aeroplane, means for automatically controlling said aeroplane including a framepivotally supported from said mounting and detachably connected to said control rod, and a rudder controlling means for said aeroplane including a pulley secured to said steering wheel concentric therewith, a pair of spaced pulleys carried between said inner and outer rings, and a cable connected to said rudder and having portions thereof guided upon said pulleys whereby a movement of said steering wheel will actuate said rudder.

14. In combination with an aeroplane, a manually operable control rod for said aeroplane, a steering wheel rotatably mounted thereon, a universal mounting for said rod comprising an outer ring pivotally mounted in said aeroplane, an inner ring pivotally supporting said control rod and having stub shafts journalled in said outer ring, means for automatically controlling said aeroplane including a frame pivotally suspended from said stub shafts, means carried by said frame for locking the same to said control rod whereby said rod and frame will move in unison, and a rudder controlling means for said aeroplane mcludmg a pulley mounted upon said steering wheel concentric there with, a pair of pulleys journalled upon said stub shafts between said inner and outer rings, and a cable having its end portions connected to said rudder, said cable having intermediate portions thereof guided upon the aforesaid pulleys whereby a rotary movement of said steering wheel will actuate said rudder.

15. In combinatlon with an aeroplane, manual control means therefor, automatic control means for said aeroplane associated with said manual means, and. means for simultaneously disconnecting said automatic means from said manual means and for'locking the former to said aeroplane.

16. In combination with an aeroplane, manual control means therefor, automatic control means for said aeroplane, a common mounting for said manual and automatic means, and means for simultaneously dis connecting said automatic means from said manual means and for locking the former to said aeroplane.

17. In combination with an manually operable control rod for said aeroplane, means for automatically controlling said aeroplane including a frame member, a common mounting for said control rod and frame member, means for locking said frame member to said control rod, and means for simultaneously rendering said locking means inoperative and for locking said frame member to said aeroplane.

18. In combination with an aeroplane, a

fuselage pivotally connected thereto,manual and automatic control means for said aeroplane,'and a single means for locking said fuselage and automatic control means to said aeroplane. V

19. In combination with an aeroplane, a fuselage pivotally connected thereto, manual and automatic control means for said aeroplane, means for locking said automatic conaeroplane, a I

trol means to said manual means, and a single means for rendering said locking means inoperative and for locking said automatic means and said fuselage to said aeroplane.

20. In combination with an aeroplane, a fuselage pivotally connected thereto, a manually operable control rod for said aeroplane, means for automatically controlling said aeroplane including a frame member, a common mounting for said control rod and frame member, means for locking said frame member to said control rod, and means for rendering said locking means inoperative and for locking said frame member and fuselage to said aeroplane.

21. In combination with an aeroplane, a fuselage pivotally connected thereto, a manually operable control rod for said aeroplane, a universal mounting for said control rod, means for automatically controlling said aeroplane including a frame member suspended from said mounting, means for looking said frame member to said control rod, and means for rendering said locking means inoperative and for locking said frame mem ber and fuselage to said aeroplane.

22. In combination with an aeroplane, a universal mounting, a manually operable control rod connected at its one end to said universal mounting, automatic control means for said aeroplane including a frame connected at its one end to said mounting, and means for detachably connecting said automatic control means to said control rod through said universal mounting.

In testimony whereof I aflix my signature.

L. MARGELIUS NORHEIM. 

